Abstract: A deployable spacecraft element which has a solar energy collection and conversion means on one side of the deployable element and a radio frequency reflecting means on the other side of the deployable element. While the solar collection and conversion means and the radio frequency reflecting means are nominally oriented in opposite spatial directions and dependent on the orientation of the spacecraft to orient for solar collection or radio frequency transmission, one or more deployable elements may be mounted to a gimbal to allow for simultaneous solar collection and radio frequency collection by the spacecraft.

Abstract: A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

Abstract: A deployable radiator panel system for a small spacecraft includes fusible metal thermal hinge having a hinge leaf affixed to a spacecraft fixed radiator panel and the corresponding hinge leaf affixed to a deployable radiator panel with fusible metal filling the interstices between knuckles of each leaf to provide a conductive heat transfer path from the spacecraft fixed radiator panel through its leaf to the intervening fusible metal and then to the deployable radiator panel leaf and finally to the deployable radiator panel. A method is provided to heat and melt the fusible metal, release the deployable radiator panel from a stowed position, apply torque to open the fusible thermal metal hinge and latch the deployable radiator panel in a deployed position, and cool and solidify fusible metal.